MINIATURE GAS TURBINE ENGINE Russian patent published in 2009 - IPC F02C3/05 

FIELD: engines and pumps.

SUBSTANCE: invention relates to gas turbine turbo-shaft and jet miniature engine of pilotless flight vehicles. The proposed miniature, primarily, single-stage engine comprises housing with air intake and exhaust holes, centrifugal micro compressor arranged inside the said housing, inflow-type microturbine and combustion chamber. There are micro holes arranged along the combustion chamber perimeter to feed fuel with flame stabiliser. The centrifugal micro compressor impeller represents a disk with radial vanes. Radial diffuser fixed vanes are located around the micro compressor impeller. The end faces of the said impeller accommodate a coating disk with its outer surface furnished with a magnetic layer. The engine housing inner surface is furnished with a stator winding. The inflow-type micro turbine impeller represents a disk with radial vanes. The radial diffuser fixed vanes are arranged around the micro turbine impeller. The end faces of the micro turbine impeller accommodate a coating disk with its outer surface furnished with a magnetic layer. The engine housing inner surface, right below the impeller coating disk is furnished with a stator winding. The said inflow-type micro turbine incorporates a nozzle box. The engine incorporates a drive. The engine housing represents a flat structure with smooth curvilinear contours of side surface. The centrifugal micro compressor represents at least two-stage, compressor made up of consecutively coupled centrifugal stages with outlet scrolls. The micro compressor centrifugal stages are arranged in one plane of the engine. The outlet scroll of the second centrifugal stage communicates with the combustion chamber. The combustion chamber outlet section terminates in a composite scroll arranged around the nozzle box radial vane circular grid. Every centrifugal stage of micro compressor has an air intake hole. That of the second centrifugal stage is provided with an adjustable valve. The said centrifugal stages communicate with each other via a through air duct furnished with an adjustable valve arranged ahead of the second stage inlet. Aforesaid through air duct features a bypass air channel communicating with the combustion chamber. Note here that the said bypass channel is furnished with adjustable valve, while every centrifugal stage of micro compressor incorporates an independent drive to control, independently, the miniature engine compression cycle.

EFFECT: higher thermodynamic efficiency of miniature gas turbine engine.

2 cl, 7 dwg